共找到 1139 条与 电气系统与设备 相关的标准,共 76 页
This SAE Aerospace Information Report (AIR) considers the issue of power regeneration into the EPS of an aircraft. A series of options for dealing with this regenerative power are considered and arranged in categories. Advantages and disadvantages of each solution, including the existing solution, are included. Validated simulation results from representative Electrical Power systems are presented in order to demonstrate how some of the solutions may operate in practice and how power quality can be maintained during regeneration. The impact on changes to the electrical generation system are also highlighted in this AIR, as these changes may have an impact o
Ways of Dealing with Power Regeneration onto an Aircraft Electrical Power System Bus
Process management for avionics - Aerospace and defence electronic systems containing lead free solder - Part 23: Rework and repair guidance to address the implications of lead-free electronics and mixed assemblies
This specification covers the general requirements for the installation and test of electronic equipment in piloted aircraft.
Installation and Test of Electronic Equipment in Aircraft, General Specification for
Civil Aircraft Electrical Installation Design Guidelines
Process management for avionics - Aerospace and defence electronic systems containing lead free solder - Part 22: Technical guidelines
Terminal Junction System, Rack Assembly, Track, Feedback Type, Series II
Connector, Receptacle External Electric Power, Aircraft, 28 Volt DC Operating Power
This part of IEC 60952 series defines the physical design@ construction and material requirements for nickel-cadmium and lead-acid aircraft batteries containing vented or valveregulated cells or monoblocs. The batteries are used for both general purposes and specific aerospace applications. The specific topics addressed in this part serve to establish acceptable quality standards required to qualify a battery as airworthy as defined in Clause 3 of IEC 60952-1:2013. A preferred range of aircraft batteries is specified in Annex A@ but this part of IEC 60952 series may be used for other battery sizes@ arrangements and ratings. For particular applications@ other design requirements may be stipulated. These will be in addition to the requirements of this part and will be covered by specific documents. It is recognised that additional data may be required by other organisations (national standards bodies@ AECMA@ SAE@ etc.). The present standard can be used as a framework to devise tests for generation of the required data
Aircraft batteries - Part 2: Design and construction requirements
This part of the IEC 60952 series defines test procedures for the evaluation@ comparison and qualification of batteries and states minimum performance and environmental levels for airworthiness. Where specific tests are defined with no pass/fail requirement (to establish performance capability)@ the manufacturer's declared values@ from qualification testing@ will be used to establish minimum requirements for ongoing maintenance of approval for that design of battery. To provide representative examples@ this standard utilises voltage and current values based upon an aircraft electrical system nominally rated at 28 V d.c. Additionally@ the nominal values for cell voltage are assumed to be 1@2 V per cell for nickel-cadmium batteries and 2@0 V per cell for lead-acid batteries. The specific topics addressed in this part of IEC 60952 serve to establish acceptable quality standards required to qualify a battery as airworthy. In cases where the requirements for a specific application exceed those detailed in this standard@ the purchaser will detail said requirements in the product specification and the method of establishing compliance. It is recognised that additional data may be required by other organisations (national standards bodies@ AECMA@ SAE etc.). The present standard can be used as a framework to devise tests for generation of the required data.
Aircraft batteries - Part 1: General test requirements and performance levels
IEC/TS 62647-21: Process management for avionics - Aerospace and defence electronic systems containing lead free solder - Part 21: Program management - Systems engineering guidelines for managing the transition to lead-free electronics
This part of IEC 60952 defines requirements for the product specification as well as procedures for a Declaration of Design and Performance (DDP) for nickel-cadmium and lead-acid aircraft batteries containing vented or valve-regulated cells or monoblocs. The batteries are used for both general purposes and specific aerospace applications. The specific topics addressed in this part serve to establish acceptable quality standards required to qualify a battery as airworthy as defined in Clause 3 of IEC 60952-1:2013. The design construction and test requirements should conform to the requirements specified in IEC 60952-1 and IEC 60952-2. It is recognised that additional data may be required by other organisations (national standards bodies@ AECMA@ SAE etc.). The present standard can be used as a framework to devise tests for generation of the required data.
Aircraft batteries - Part 3: Product specification and declaration of design and performance (DDP)
This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This specification has been declared ""NONCURRENT"" as of April 2008. It is recommended, therefore, that this document not be specified for new designs. This specification covers the general requirements for the design and construction of air/gas compressor units (see 6.4.1). The detail requirements for a particular air compressor unit shall be as specified in the individual equipment specification for that particular air
Compressor Units, Air/Gas, General Requirements For
This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This specification covers general requirements for direct current electrically held, environmentally sealed toggle switches for use in alternating current (AC) and direct current (DC) applications.
Switches, Toggle, Electrically Head, Sealed, General Specification for
This Technical Report provides information when using semiconductor devices in wider temperature ranges than those specified by the device manufacturer. The uprating solutions described herein are considered exceptions, when no reasonable alternatives are available;otherwise devices are utilized within the manufacturers'specifications.
Process management for avionics - Electronic components capability in operation - Part 1: Temperature uprating
Aerospace - Wire, aluminium alloy and copper-clad aluminium conductors - General performance requirements
This document has been declared ""Stabilized"" and will no longer be subjected to periodic reviews for currency. Users are responsible for verifying references and continued suitability or technical requirements. New technology may exist. This specification covers two types of drive couplings for magnetos as follows: 1. 17-tooth coupling and 2. 33-tooth coupling. This specification also covers three types of magneto shaft ends as follows: 1. tapered shaft end; 2. 6-tooth spline shaft; and 3. 24-tooth spline shaft.
Magnetos, Aircraft, Drives for
Aerospace series. Electrical cables, installation. Protective sleeves in meta-aramid fibres. Self-wrapping shielded (EMI) protective sleeve with nickel copper braid, flexible post installation operating temperature from -55°C to 200°C. Product standard
Aerospace series. Cable outlet accessories for circular and rectangular electrical and optical connectors. Manual installation tool, style Z, for installation of stainless steel shield termination band EN 3660-033, to cable outlet accessories. Product sta
This SAE Aerospace Standard standardizes practices to: a. maximize availability of authentic parts, b. procure parts from reliable sources, c. assure authenticity and conformance of procured parts, d, control suspect or confirmed fraudulent/counterfeit EEE parts, e. and report suspect or confirmed fraudulent/counterfeit EEE parts to other potential users and Authority Having Jurisdiction; f. and assess.mitigate, control, and report parts which have been used, refurbished, or reclaimed, but represented as new product.
Fraudulent/Counterfeit Electronic Parts; Avoidance, Detection, Mitigation, and Disposition
This SAE Aerospace Information Report (AIR) provides methodologies and approaches that have been used to install and integrate full-authority-digital-engine-control (FADEC) systems on transport category aircraft. Although most of the information provided is based on turbofan engines installed on large commercial transports, many of the issues raised are equally applicable to corporate, general aviation, regional and commuter aircraft, and to military installations, particularly when commercial aircraft are employed by military users. The word ""engine"" is used to designate the aircraft propulsion system. The engine station designations used in this report.
Guidelines for the Integration of Electronic Engine Control Systems with Transport Category (Part 25) and General Aviation (Part 23) Aircraft
Copyright ©2007-2022 ANTPEDIA, All Rights Reserved
京ICP备07018254号 京公网安备1101085018 电信与信息服务业务经营许可证:京ICP证110310号